Abstract The interactions between shock waves and boundary layer are commonplace in hypersonic aerodynamics. They represent a very challenging design issue for hypersonic vehicle. A typical example of shock wave boundary layer interaction is the flowfield past aerodynamic surfaces during control. As a consequence, such flow interaction phenomena influence both vehicle aerodynamics and aerothermodynamics. In this framework, the present research effort describes the numerical activity performed to simulate the flowfield past a deflected flap in hypersonic flowfield conditions for a winged re-entry vehicle.
Highlights Computational Fluid Dynamics (CFD) in Hypersonics. Interactions between shock waves and boundary layer. Shock wave boundary layer interaction is the flowfield past aerodynamic surfaces during control. Hypersonic flowfield analysis for a winged re-entry vehicle. Overheating and pressure overshoot on aerodynamic control surfaces.
Flap effectiveness appraisal for winged re-entry vehicles
Acta Astronautica ; 122 ; 175-184
2015-12-30
10 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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